CN108225711A - A kind of thermally protective materials antiscour test bracket - Google Patents
A kind of thermally protective materials antiscour test bracket Download PDFInfo
- Publication number
- CN108225711A CN108225711A CN201711347405.2A CN201711347405A CN108225711A CN 108225711 A CN108225711 A CN 108225711A CN 201711347405 A CN201711347405 A CN 201711347405A CN 108225711 A CN108225711 A CN 108225711A
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- CN
- China
- Prior art keywords
- antiscour
- test bracket
- protective materials
- thermally protective
- section
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention relates to a kind of thermally protective materials antiscour test bracket, tool is triangle there are two cavity, a cavity cross section, another cavity cross section is inverted trapezoidal, and triangle base connects with inverted trapezoidal long side, and vertex angle has leading edge, and section is sector.The heat structure of the present invention, rigid thermal insulation tile and flexible heat insulation felt antiscour test bracket, its is simple for structure, it assembles easy to operate, realize heat structure, rigid thermal insulation tile and flexible heat insulation felt antiscour experiment, the requirement that complete machine antiscour tests and meets all antiscour experiments is simplified, there is larger actual application value.
Description
Technical field
The invention belongs to Aeronautics and Astronautics and near space technical field, are related to a kind of heat structure, rigid thermal insulation tile and flexibility
The antiscour test bracket of the thermally protective materials such as heat insulation felt.
Background technology
Re-entry space vehicle, hypersonic aircraft flying speed are high, and Aerodynamic Heating effect is big, and inside loads a large amount of system
Equipment, these system equipments substantially work under lower temperature environments, and this requires body outer surface has heat insulating function；
Meanwhile the thermally protective materials such as heat structure, rigid thermal insulation tile and flexible heat insulation felt, under aerodynamic load effect, surface is damaged
Bad possibility, it is therefore desirable to carry out heat structure, rigid thermal insulation tile and flexible heat insulation felt antiscour experiment, by experimental result come into
Row demonstration；And the antiscour experimental cost of complete machine is high, the period is long, is unfavorable for experimental study, thus be badly in need of a kind of simplification, have
Representative testpieces carries out experimental demonstration.
Still in development phase, various experimental pieces and stent are also immature for domestic re-entry space vehicle, hypersonic aircraft,
It there is no referential ready-made technology.
Invention content
In view of the deficienciess of the prior art, the purpose of the present invention is to propose to a kind of thermally protective materials antiscour experiment branch
Frame.
The technical solution that the present invention takes is a kind of thermally protective materials antiscour test bracket, is frame structure, has
There are two cavity, a cavity cross section is triangle, another cavity cross section is inverted trapezoidal, triangle base and inverted trapezoidal long side
Connect, vertex angle has leading edge, and section is sector.
Groove is equipped in the middle part of above-mentioned leading edge.
Above-mentioned test bracket material is aluminium alloy.
Above-mentioned cavity outer mold surface is equipped with circular hole, as pressure measurement channel.
Advantageous effect：This test bracket adds the mode of production using whole numerical control machine；It is recessed using four planes and a head
It falls into and places heat structure, rigid thermal insulation tile and flexible heat insulation felt respectively；According to the gap clearance of different size thermal insulation tiles, in metal branch
Circular hole is opened up on frame as pressure measurement channel, for re-entry space vehicle, hypersonic aircraft provide body surface heat structure,
Rigid thermal insulation tile and flexible heat insulation felt antiscour test bracket.And this supporting structure is simple and can meet heat structure, rigidly heat-insulated
Watt and flexible heat insulation felt antiscour experiment all demands.
Description of the drawings
Fig. 1 is stereoscopic schematic diagram of the present invention；
Fig. 2 structure diagrams during experiment for the present invention；
Fig. 3 is Fig. 2 sectional views；Wherein, 1：Heat structure；2：Windward side rigidity thermal insulation tile；3：Windward side flexibility heat insulation felt；4：
Leeward rigidity thermal insulation tile；5：Leeward flexibility heat insulation felt；6：Test bracket；7：Multiple material plate.
Specific embodiment
The present invention is described in further detail with reference to the accompanying drawings of the specification.
A kind of thermally protective materials antiscour test bracket, is frame structure, and tool is three there are two cavity, a cavity cross section
Angular, another cavity cross section is inverted trapezoidal, and triangle base connects with inverted trapezoidal long side, and vertex angle has leading edge, is cut
Face is sector, as shown in Figure 1, during experiment, air-flow is washed away from leading edge to stent rear, and triangular cavity two sides form
Windward side, inverted trapezoidal cavity two sides form leeward.
In order to carry out antiscour experiment to heat structure, groove is equipped in the middle part of above-mentioned leading edge, for placing heat structure, heat structure
Material requirements heat resistanceheat resistant performance is best, for worst environment, therefore is positioned over the front end of air-flow.
The weight of above-mentioned mitigation test bracket, test bracket material are aluminium alloy, disclosure satisfy that intensity, the synthesis of cost will
It asks.
Above-mentioned cavity outer mold surface is equipped with circular hole, as pressure measurement channel.
During experiment, test bracket 6 is fixed on wind tunnel test frame first, 6 windward side of test bracket and leeward
Face and the multiple rivet interlacement of material plate 7, windward side rigidity thermal insulation tile 2 and windward side flexibility heat insulation felt 3 are met by being glued to be fixed on
On wind face, leeward rigidity thermal insulation tile 4, leeward flexibility heat insulation felt 5 are fixed on by being glued on windward side, heat structure 1, such as
C-SiC thin slices are then positioned over groove and are directly glued with test bracket, as shown in Figure 2,3, after installing thermally protective materials, vacuum
Pressurization, for 24 hours after, to test bracket carry out wind tunnel test, data, Circularhole diameter are collected by the circular hole of cavity outer mold surface
For 1.2mm.
Claims (4)
1. a kind of thermally protective materials antiscour test bracket, it is characterised in that：For frame structure, there are two cavity, a skies for tool
Chamber section is triangle, another cavity cross section is inverted trapezoidal, and triangle base connects with inverted trapezoidal long side, vertex angle tool
There is leading edge, section is sector.
2. thermally protective materials antiscour test bracket according to claim 1, it is characterised in that：It is equipped in the middle part of leading edge recessed
Slot.
3. thermally protective materials antiscour test bracket according to claim 1, it is characterised in that：Test bracket material is aluminium
Alloy.
4. thermally protective materials antiscour test bracket according to claim 1, it is characterised in that：Cavity outer mold surface is equipped with circle
Hole, as pressure measurement channel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711347405.2A CN108225711B (en) | 2017-12-15 | 2017-12-15 | Thermal protection material antiscour test support |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711347405.2A CN108225711B (en) | 2017-12-15 | 2017-12-15 | Thermal protection material antiscour test support |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108225711A true CN108225711A (en) | 2018-06-29 |
| CN108225711B CN108225711B (en) | 2020-10-20 |
Family
ID=62652209
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711347405.2A Active CN108225711B (en) | 2017-12-15 | 2017-12-15 | Thermal protection material antiscour test support |
Country Status (1)
| Country | Link |
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| CN (1) | CN108225711B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105223006A (en) * | 2015-09-17 | 2016-01-06 | 中国运载火箭技术研究院 | A kind of actuation means of power test run body wing flap antiscour test and test method |
| CN106516072A (en) * | 2016-11-10 | 2017-03-22 | 清华大学 | Thermal protection structure for leading edge of hypersonic vehicle |
| CN106547965A (en) * | 2016-10-31 | 2017-03-29 | 湖北航天技术研究院总体设计所 | A kind of temperature barrier of hypersonic gliding class aircraft |
| CN206339360U (en) * | 2016-11-23 | 2017-07-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of arc tunnel treadmill test model support |
-
2017
- 2017-12-15 CN CN201711347405.2A patent/CN108225711B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105223006A (en) * | 2015-09-17 | 2016-01-06 | 中国运载火箭技术研究院 | A kind of actuation means of power test run body wing flap antiscour test and test method |
| CN106547965A (en) * | 2016-10-31 | 2017-03-29 | 湖北航天技术研究院总体设计所 | A kind of temperature barrier of hypersonic gliding class aircraft |
| CN106516072A (en) * | 2016-11-10 | 2017-03-22 | 清华大学 | Thermal protection structure for leading edge of hypersonic vehicle |
| CN206339360U (en) * | 2016-11-23 | 2017-07-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of arc tunnel treadmill test model support |
Non-Patent Citations (1)
| Title |
|---|
| 张志刚: "高超声速飞行器热防护***设计方法", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
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| Publication number | Publication date |
|---|---|
| CN108225711B (en) | 2020-10-20 |
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